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公开(公告)号：US11028713B2
公开(公告)日：2021-06-08
申请号：US16373876
申请日：2019-04-03
Applicant: United Technologies Corporation
Inventor： Scot A. Webb
Abstract: A gas turbine engine assembly includes a compressor including a plurality of rotors, where at least one of the plurality of rotors includes a radial inner sealing surface. A rotating shaft drives rotation of the plurality of rotors, where the rotating shaft includes an annular groove proximate the radial inner sealing surface. A seal is disposed within the annular groove, and the seal comprises at least two annular sections forming a complete circumference. Each of the at least two annular sections are separate parts and include a radially-facing sealing surface engaged to the radial inner sealing surface of the rotor and an annular slot disposed radially inward of the radially-facing sealing surface. A retainer is disposed within the annular slot limiting radial expansion of the at least two annular sections.
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公开(公告)号：US10100732B2
公开(公告)日：2018-10-16
申请号：US14765760
申请日：2013-12-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas W. Ward , Scot A. Webb , Isaac Jon Hogate
CPC classification number: F02C7/047 , F01D15/10 , F01D25/02 , F02C7/32 , F05D2220/76 , H02K7/1823 , H05B3/0014 , H05B3/06
Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.
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公开(公告)号：US20170023010A1
公开(公告)日：2017-01-26
申请号：US15039929
申请日：2014-11-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee Drozdenko , James O. Hansen , Jesse C. Meyer , Maria C. Kirejczyk , Scot A. Webb , Brandon A. Gates , Richard B. Bergethon
CPC classification number: F04D29/388 , B32B5/024 , B32B7/12 , B32B15/14 , B32B15/20 , B32B2262/101 , B32B2603/00 , F01D5/12 , F01D5/14 , F01D5/147 , F01D5/28 , F01D5/282 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/325 , F05D2220/36 , F05D2240/303 , F05D2300/121 , F05D2300/133 , F05D2300/6012
Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.
Abstract translation: 叶片包括从后缘延伸到前缘的翼型件。 翼型件包括由含铝材料形成的主体。 护套位于前缘，由含钛材料形成。 三明治位于护套和翼型体之间，夹层包括邻近护套的外部粘合剂层，中间织物层和邻近身体的内部粘合剂层。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US11441592B2
公开(公告)日：2022-09-13
申请号：US15981590
申请日：2018-05-16
Applicant: United Technologies Corporation
Inventor： Kevin Kassel , Scot A. Webb
Abstract: A locking plate for restricting rotation of a fastener connecting a first component of a gas turbine engine and a second component of a gas turbine engine includes a base having a planar surface receivable in overlapping arrangement with a head of the fastener. A locking portion extends from the base. Engagement between the locking portion and the first component restricts rotation of the locking portion. A key extends from the base and is connectable to the fastener such that the fastener is not rotatable relative to the key when the locking portion has engaged the first component.
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公开(公告)号：US10982683B2
公开(公告)日：2021-04-20
申请号：US15039929
申请日：2014-11-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee Drozdenko , James O. Hansen , Jesse C. Meyer , Maria C. Kirejczyk , Scot A. Webb , Brandon A. Gates , Richard B. Bergethon
IPC: F04D29/38 , B32B7/12 , F01D5/28 , F01D5/14 , F01D5/12 , B32B5/02 , B32B15/14 , B32B15/20 , F04D29/02 , F04D29/32
Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US09951691B2
公开(公告)日：2018-04-24
申请号：US14765760
申请日：2013-12-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas W. Ward , Scot A. Webb , Isaac Jon Hogate
Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.
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公开(公告)号：US20160222978A1
公开(公告)日：2016-08-04
申请号：US14917476
申请日：2014-08-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee M. Drozdenko , James O. Hansen , Jesse C. Meyer , John J. Marcin, JR. , Robert M. Shemenski , Scot A. Webb , Brandon A. Gates , Michael A. Morden
Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A plurality of separate spacers (320; 380; 400) are between the sheath and the substrate and have a plurality of gaps between the spacers.
Abstract translation: 翼型件（100）包括沿翼型件的翼型（102）的至少一部分具有基底（120）。 护套（122）具有容纳衬底的一部分（160）的通道（144）。 多个分离的间隔物（320; 380; 400）位于护套和衬底之间并且在间隔件之间具有多个间隙。
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公开(公告)号：US20150377129A1
公开(公告)日：2015-12-31
申请号：US14765760
申请日：2013-12-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas W. Ward , Scot A. Webb , Isaac Jon Hogate
CPC classification number: F02C7/047 , F01D15/10 , F01D25/02 , F02C7/32 , F05D2220/76 , H02K7/1823 , H05B3/0014 , H05B3/06
Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.
Abstract translation: 公开了用于除燃气涡轮发动机的风扇的系统和方法。 系统和方法可以包括与风扇的第一旋转表面可操作地相关联的电线圈; 与风扇的第二旋转表面可操作地相关联的磁体，所述第二旋转表面在与所述第一旋转表面相反的方向上旋转，所述磁体和所述电线圈在所述风扇运动时产生电力; 以及与风扇上的表面可操作地相关联的加热元件，加热元件由由磁体和电线圈产生的电力驱动。
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公开(公告)号：US20150292342A1
公开(公告)日：2015-10-15
申请号：US14644596
申请日：2015-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark David Ring , Scot A. Webb , Mark J. Rogers , Gerald D. Cassella , Charles H. Warner , Eric A. Kuehne , Jonathan J. Earl , Matthew M. Zietala , Neil L. Tatman , Randall J. Butcher , Matthew R. Willett , Nicholas R. Leslie
CPC classification number: F01D9/041 , F01D9/042 , F01D25/246 , F05D2220/32 , F05D2230/61 , F05D2240/12 , F05D2240/80 , Y02T50/672
Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to said second end-of-cluster vane; and a multiple of base vanes between said first end-of-cluster vane and said neighbor vane.
Abstract translation: 用于燃气涡轮发动机的叶片组包括第一端簇叶片，第二端簇叶片，与所述第二端簇叶片相邻的相邻叶片; 以及在所述第一端部叶片叶片和所述相邻叶片之间的多个基部叶片。
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公开(公告)号：US20190353197A1
公开(公告)日：2019-11-21
申请号：US15981590
申请日：2018-05-16
Applicant: United Technologies Corporation
Inventor： Kevin Kassel , Scot A. Webb
Abstract: A locking plate for restricting rotation of a fastener connecting a first component of a gas turbine engine and a second component of a gas turbine engine includes a base having a planar surface receivable in overlapping arrangement with a head of the fastener. A locking portion extends from the base. Engagement between the locking portion and the first component restricts rotation of the locking portion. A key extends from the base and is connectable to the fastener such that the fastener is not rotatable relative to the key when the locking portion has engaged the first component.
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